Turbine engine with interlocking seal

ABSTRACT

A turbine engine with an outer rotor that circumscribes an inner rotor or inner stator. The outer rotor includes circumferentially arranged components with a radial outer end and radial inner end. Inner ends of confronting sides of adjacent components include at least one damper element to dampen the relative motion of the components or to provide at least a partial seal between adjacent components.

CROSS-REFERENCE TO RELATED APPLICATION(S)

This application claims priority to Italian Application No.102019000013854, filed Aug. 2, 2019, which is incorporated herein byreference its entirety.

The project leading to this application has received funding from theClean Sky 2 Joint Undertaking under the European Union's Horizon 2020research and innovation program under grant agreement No.CS2-LPA-GAM-201e 8/2019-01.

TECHNICAL FIELD

This disclosure generally relates to a turbine engine with an outerrotor that circumscribes an inner rotor or inner stator and morespecifically relates to the dampening or sealing of adjacent componentscoupled to the outer rotor.

BACKGROUND

Turbine engines, and particularly gas or combustion turbine engines, arerotary engines that extract energy from a flow of combusted gasespassing through the engine onto a multitude of rotating turbine blades.

A turbine engine includes but is not limited to, in serial flowarrangement, a forward fan assembly, an aft fan assembly, ahigh-pressure compressor for compressing air flowing through the engine,a combustor for mixing fuel with the compressed air such that themixture may be ignited, and a high-pressure turbine. The high-pressurecompressor, combustor and high-pressure turbine are sometimescollectively referred to as the core engine. In operation, the coreengine generates combustion gases which are discharged downstream to acounter-rotating low-pressure turbine that extracts energy therefrom forpowering the forward and aft fan assemblies.

In at least some turbine engines, at least one turbine rotates in anopposite direction than the other rotating components within the engine.In some implementations a counter-rotating low-pressure turbine includesan outer drum having a first set of stages that are rotatably coupled tothe forward fan assembly, and an inner drum having an equal number ofstages that is rotatably coupled to the aft fan assembly.

Counter rotating blades present challenges and a need for better sealingor dampening between the circumferentially arranged rotating portionscoupled to the outer rotor. For example, improved sealing or dampeningbetween the inner ends of circumferentially arranged airfoils coupled tothe outer rotor.

BRIEF DESCRIPTION

In one aspect, the present disclosure relates to a turbine engine thatincludes an inner rotor/stator having a longitudinal axis, an outerrotor circumscribing at least a portion of the inner rotor/stator androtating about the longitudinal axis, and having at least one componentcomprising a plurality of circumferentially arranged and radiallyextending component segments, each component segment having first andsecond ends, and a damper element securing the first and second ends toeach other.

BRIEF DESCRIPTION OF THE DRAWINGS

In the drawings:

FIG. 1 is a schematic cross-sectional diagram of a turbine engine with acounter rotating low pressure turbine for an aircraft.

FIG. 2 is an enlarged schematic view of a portion of an outer rotor andblades of the counter rotating low pressure turbine of FIG. 1.

FIG. 3 is a cross section of an inner band from the blades of FIG. 2taken at a seal.

FIG. 4 is another cross section of the inner band from the blades ofFIG. 2 taken at the seal.

FIG. 5 is yet another cross section of the inner band from the blades ofFIG. 2 taken at the seal.

FIG. 6 is another enlarged schematic view of a portion of an outer rotorand blades of the counter rotating low pressure turbine of FIG. 1.

FIG. 7 is an exploded view of a damper element and the adjacent bladesfrom FIG. 6.

FIG. 8 is yet another enlarged schematic view of a portion of an outerrotor and blades of the counter rotating low pressure turbine of FIG. 1.

FIG. 9 is an enlarged schematic view of a portion the blades of FIG. 8.

FIG. 10 is a cross section of an inner band from the blades of FIG. 8,taken at a fastener.

DETAILED DESCRIPTION

Aspects of the disclosure described herein are directed to the sealingor dampening of circumferentially arranged components coupled to anouter rotor, where the outer rotor circumscribes an inner rotor/stator.For purposes of illustration, the present disclosure will be describedwith respect to a counter rotating low pressure turbine for an aircraftturbine engine. It will be understood, however, that aspects of thedisclosure described herein are not so limited and may have generalapplicability within an engine, including, but not limited to, lowpressure turbines with stationary stator components or counter-rotatingportions of the engine located in positions other than the low pressureturbine portion. It will be further understood that aspects of thedisclosure described herein are not so limited and may have generalapplicability in non-aircraft applications, such as other mobileapplications and non-mobile industrial, commercial, and residentialapplications.

As used herein, the term “upstream” refers to a direction that isopposite the fluid flow direction, and the term “downstream” refers to adirection that is in the same direction as the fluid flow. The term“fore” or “forward” means in front of something and “aft” or “rearward”means behind something. For example, when used in terms of fluid flow,fore/forward means upstream and aft/rearward means downstream.Additionally, as used herein, the terms “radial” or “radially” refer toa direction away from a common center. For example, in the overallcontext of a turbine engine, radial refers to a direction along a rayextending between a center longitudinal axis of the engine and an outerengine circumference. Furthermore, as used herein, the term “set” or a“set” of elements can be any number of elements, including only one.

All directional references (e.g., radial, axial, proximal, distal,upper, lower, upward, downward, left, right, lateral, front, back, top,bottom, above, below, vertical, horizontal, clockwise, counterclockwise,upstream, downstream, forward, aft, etc.) are only used foridentification purposes to aid the reader's understanding of the presentdisclosure, and do not create limitations, particularly as to theposition, orientation, or use of aspects of the disclosure describedherein. Connection references (e.g., attached, coupled, secured,fastened, connected, and joined) are to be construed broadly and caninclude intermediate members between a collection of elements andrelative movement between elements unless otherwise indicated. As such,connection references do not necessarily infer that two elements aredirectly connected and in fixed relation to one another. The exemplarydrawings are for purposes of illustration only and the dimensions,positions, order and relative sizes reflected in the drawings attachedhereto can vary.

FIG. 1 is a schematic cross-sectional diagram of a turbine engine 10 foran aircraft. The turbine engine 10 has a centerline or longitudinal axis12 extending forward 14 to aft 16. The turbine engine 10 includes, indownstream serial flow relationship, a fan section 18 including aforward fan assembly 20 and an aft fan assembly 21, a compressor section22 including a booster or low pressure (LP) compressor 24 and a highpressure (HP) compressor 26, a combustion section 28 including acombustor 30, a turbine section 32 including a HP turbine 34, and acounter-rotating LP turbine 36, and an exhaust section 38.

The fan assemblies 20 and 21 are positioned at a forward end of theturbine engine 10 as illustrated. The terms “forward fan” and “aft fan”are used herein to indicate that one of the fans 20 is coupled axiallyupstream from the other fan 21. It is also contemplated that the fanassemblies 20, 21 can be positioned at an aft end of turbine engine 10.Fan assemblies 20 and 21 each include a plurality of rows of fan blades40 positioned within a fan casing 42. The fan blades 40 are joined torespective rotor disks 44 that are rotatably coupled through arespective forward fan shaft 46 to the forward fan assembly 20 andthrough an aft fan shaft 47 to the aft fan assembly 21.

The HP compressor 26, the combustor 30, and the HP turbine 34 form anengine core 48 of the turbine engine 10. The engine core 48 issurrounded by a shroud or outer casing 49 defining an interior 50, whichcan be coupled with the fan casing 42. The HP turbine 34 is coupled tothe HP compressor 26 via a core rotor or shaft 52. In operation, theengine core 48 generates combustion gases that are channeled downstreamto the counter-rotating LP turbine 36 which extracts energy from thegases for powering fan assemblies 20, 21 through their respective fanshafts 46, 47.

The counter-rotating LP turbine 36 includes an outer rotor 54 positionedradially inward from outer casing 49. The outer rotor 54 can have agenerally frusto-conical shape. The outer rotor 54 can include at leastone component that includes a plurality of circumferentially arrangedcomponent segments, illustrated by example as a first set of airfoils 55comprised of a plurality of circumferentially arranged airfoils 57 thatextend radially inwardly from the outer rotor 54 towards thelongitudinal axis 12. The first set of airfoils 55 can be a first set ofrotating blades comprised of a plurality of circumferentially arrangedblades. Alternatively, the first set of airfoils 55 can becircumferentially arranged stationary blades or vanes, where a pair ofstationary blades or vanes can form a nozzle.

The counter-rotating LP turbine 36 further includes an innerrotor/stator 60 that is at least in part circumscribed by the outerrotor 54. The inner rotor/stator 60 can be stationary or rotatedepending on the particular engine configuration. As illustrated by wayof example, the inner rotor/stator 60 is arranged substantiallycoaxially with respect to, and radially inward of the outer rotor 54.The inner rotor/stator 60 includes a second set of airfoils 62 withairfoils 64, circumferentially arranged, where each airfoil 64 extendsradially outwardly away from the longitudinal axis 12. The second set ofairfoils 62 can be a first set of rotating blades comprised of aplurality of circumferentially arranged blades. Alternatively, thesecond set of airfoils 62 can be stationary blades or vanes, where apair of stationary blades or vanes can form a nozzle.

The first and second sets of airfoils 55, 62 define a plurality ofturbine stages 66. While illustrated as having five stages, it should beunderstood that any quantity of stages is contemplated and the stagesshown are for illustrative purposes and not meant to be limiting.

While illustrated as having a counter-rotating LP turbine 36, it shouldbe understood that aspects of the disclosure discussed herein can beapplied to turbine engines without counter-rotating LP turbines. Turbineengines having LP turbines in which static circumferentially arrangedvanes are axially spaced from rotating circumferentially arranged bladesare also contemplated. Furthermore, it is also contemplated that thecompressor section 22, in particular either the LP compressor 24 or theHP compressor 26 of the turbine engine 10, can counter-rotate.

FIG. 2 is an enlarged schematic view of a portion of the outer rotor 54and the first set of airfoils 55, where the first set of airfoils areillustrated, by way of example, as the first set of blades 56. The outerrotor 54 can form an outer band 68 from which the first set of blades 56extend. Each of the airfoils 57 or blades 58 of the first set of blades56 has a first circumferential end 70 and a second circumferential end72, where the first and second circumferential ends 70, 72 of adjacentblades 58 form confronting pairs 74 of first and second circumferentialends 70, 72. An outer end 76 of each of the blades 58 is radially spacedfrom an inner end 78, where the outer end 76 can be coupled to the outerband 68.

A radial damper element 80 can secure the inner ends 78 of at least theadjacent blades 58 or confronting pairs 74. An inner band 82 can beformed from the connecting of the inner ends 78 of the confronting pairs74 the damper element 80. The damper element 80 can include a firstchannel 84 on the first circumferential end 70, a second channel 86 onthe second circumferential end 72, and an interlocking seal or a seal88. The seal 88 can reside in both the first and second channels 84, 86.A confronting channel pair 90 can be defined by first and secondchannels 84, 86 that are generally aligned and confronting.

FIG. 3 is a cross section of the inner band 82, with the blade 58removed for clarity, taken at the seal 88, illustrated, by way ofnon-limiting example as the first channel 84 in the firstcircumferential end 70. The first channel 84 is a circumferential recessthat extends in a radial direction, having a radial channel length 94. Achannel opening 96 can be defined in the plane of the firstcircumferential end 70, where the channel opening 96 is generally shapedas a stadium or obround.

The first channel 84 receives at least a portion of the seal 88 having aradial seal length of 98. The radial seal length of 98 is less than theradial channel length 94, defining a gap 100.

A protruding portion 102 of the seal 88 can be received by the secondchannel 86 (not shown). It is contemplated that the second channel 86 inthe second circumferential end 72 would be similar to the first channel84, so that the confronting channel pair 90 would extend in the radialdirection.

In operation, the damper element 80 can secure the inner ends 78 of atleast the adjacent blades 58 extending from the outer rotor 54. Thedamper element 80 secures the inner ends 78 using the seal 88 seated ineach confronting channel pair 90 of the confronting pairs 74. The damperelement 80 dampens the relative movement of the blades 58 whose innerends 78 are connected or secured with the seal 88. The relative movementcan include, but is not limited to relative radial movement, relativetangential movement, or relative axial movement. The damper element 80can also be used to direct, prevent, or control airflow, for example,between the blades 58. It is contemplated that the damping element 80 orthe seal 88 can dissipate kinetic energy from the inner ends 78 of theblades 58. It is further contemplated, by way of non-limiting example,that the seal 88, at least in part, can include nickel, cobalt basealloys, ceramic material, or any combination therein.

FIG. 4 is another example of a cross section of the inner band 82 takenat a seal 188. The seal 188 is similar to the seal 88, therefore, likeparts will be identified with like numerals increased by 100, with itbeing understood that the description of the like parts of the seal 88applies to the seal 188, unless otherwise noted. The seal 188 isreceived by a first channel 184 in the first circumferential end 70. Achannel opening 196 can have a similar shape to a cross or rectangularcross section of the first channel 184.

FIG. 5 is yet another example of a cross section of the inner band 82taken at a seal 288. The seal 288 is similar to the seal 88, therefore,like parts will be identified with like numerals increased by 200, withit being understood that the description of the like parts of the seal88 applies to the seal 288, unless otherwise noted. An upper channel 289or a lower channel 291 can be formed in the first circumferential end70. The upper channel 289 can receive an upper seal 293, while the lowerchannel 291 can receive a lower seal 295. It is contemplated thatcomplementing upper or lower channels are located in the secondcircumferential end 72 (not shown) that can receive the upper or lowerseals 293, 295, respectively. The upper or lower seals 293, 295 can beused in addition to the seal 288 received by a first channel 284. It iscontemplated that any number of seals can reside in the inner band 82 tosecure the inner ends 78.

It is contemplated that the seal(s) 88, 188, 288, 293, 295 residing inthe first and second channels 84, 86, 184, upper channels 289, or lowerchannels 291 can have any shape. It is further contemplated that morethan one seal can reside in the confronting channel pairs 90.

It is contemplated that the first channel 84, 184, 284 can be havedifferent shapes or dimensions than the second channel 86 and still bealigned and confronting.

FIG. 6 is another enlarged schematic view of a portion of an outer rotor354 and a first set of blades 356. The outer rotor 354 and the first setof blades 356 is similar to the outer rotor 54 and the first set ofblades 56, therefore, like parts will be identified with like numeralsincreased by 300, with it being understood that the description of thelike parts of the outer rotor 54 and the first set of blades 56 appliesto the outer rotor 354 and the first set of blades 356, unless otherwisenoted.

Each of the plurality of circumferential blades 358 of the first set ofblades 356 includes a passage segment 359. The passage segment 359extends between and opens onto a first circumferential end 370 and asecond circumferential end 372. The passage segment 359 can be locatedin an inner band 382 used to secure an inner end 378 of each of theplurality of circumferential blades 358.

A first opening 373 can be defined by the passage segment 359 opening atthe first circumferential end 370. A second opening 375 can be definedby the passage segment 359 opening at the second circumferential end372. A confronting open pair 377 is defined by the first and secondopenings 373, 375 of adjacent blades 358.

A radial damper element 381 can include a tube 383 that extends betweenthe first and second opening 373, 375 of the confronting open pair 377.The tube 383 can extend only partially into the passage segments 359 theconfronting open pair 377. Alternatively, the tube 383 can extendthrough a circumferential passage 379 formed from the collection of thepassage segments 359 in the first set of blades 356. The circumferentialpassage 379 can circumscribe the inner band 382. It is contemplated thatthe tube 383 can be any number of pieces of tubing, including one. It isfurther contemplated that the tube 383 can be any length including, butno limited to, the length of the circumferential passage 379.

The tube 383 includes a spacer 385 located between confronting pairs 374of first and second confronting ends. That is, the spacer 385 is locatedbetween or is used to maintain separation of the inner ends 378 thefirst and second confronting ends 370, 372. While illustrated as a ridgeor detent, the spacer 385 can have any shape and circumscribe a portionof the tube 383. Alternatively, the spacer 385 can circumscribe theentire circumference of the tube 383. The spacer 385 can be used to helplocated the tube 383 with respect to the adjacent blades 358.Additionally or alternatively, the spacer 385 can provide a barrier tomaintain a minimum distance between the first and second confrontingends 370, 372.

FIG. 7 is an exploded view of adjacent blades 358 with the damperelement 381. A tube cross-section profile 387 can be obtained from thelargest dimension of the cross section of the tube 383. A passagecross-section profile 389 can be obtained from the largest dimension ofthe cross section of the passage segment 359. The damper element 381dampens the relative movement of the blades 358 whose inner ends 378 areconnected or secured with the tube 383. The relative movement caninclude, but is not limited to relative radial movement, relativetangential movement, or relative axial movement. The damper element 381can also be used to direct, prevent, or control airflow, for example,between the blades 358. It is contemplated that the damping element 381or the tube 383 can dissipate kinetic energy from the inner ends 378 ofthe blades 358. It is further contemplated, by way of non-limitingexample, that the tube 383 can, at least in part, include nickel, cobaltbase alloys, ceramic material, or any combination therein.

FIG. 8 is yet another enlarged schematic view of a portion of an outerrotor 454 and a first set of blades 456. The outer rotor 454 and thefirst set of blades 456 is similar to the outer rotor 54 and the firstset of blades 56, therefore, like parts will be identified with likenumerals increased by 400, with it being understood that the descriptionof the like parts of the outer rotor 54 and the first set of blades 56applies to the outer rotor 454 and the first set of blades 456, unlessotherwise noted.

A radial damper element 431 couples inner ends 478 of circumferentiallyadjacent inner ends 478 of the blades 458. The damper element 431 caninclude a bracket 433 that can be attached to or formed with the blade458. The bracket 433 can include a radially extending flange 435 thatcouples to a ring 437. The ring 437 secures the inner ends 478 of thefirst set of blades 456. An inner band can be defined by the inner ends478 with the radially extending flanges 435 to which the ring 437mounts.

As illustrated, by way of non-limiting example, the ring 437 cancircumscribe an inner band 482. Alternatively, the ring 437 can includeone or more regions that can expand, contract, or provide a gap forexpansion or contraction.

A fastener 439 can couple the radially extended flange 435 to thebracket 433. The fastener 439 can be a bolt, pin, screw, nail, clip,hook, or any other known fastening device or combination thereof.Alternatively, the radially extended flange 435 can be attached to theblade 458 using known adhesive or bonding methods or materials, such as,but not limited to, welding, melting, pressure fitting, or unitaryformation. Optionally, a honeycomb wear pad 447 can be mounted to theradially extending flange 435 or the ring 437.

FIG. 9 is an enlarged schematic view of a portion of the blade 458further illustrating the bracket 433 with radially extending flange 435.An aperture 441 or pass in the bracket 433 or inner end 478 can receivethe fastener 439. The fastener 439 can have a fastener cross-sectionalshape 443, illustrated by way of non-limiting example as a circle. Theaperture 441 can have an aperture cross-sectional shape 445, illustratedby way of non-limiting example as ovate. It is contemplated that thefastener cross-sectional shape 443 and the aperture cross-sectionalshape 445 can have similar or different cross-sectional shapes. It isfurther contemplated that the aperture 441 can be oversized relative tothe fastener 439.

FIG. 10 is a cross section of the inner band 482 taken at the fastener439. The fastener 439 can pass through the aperture 441 to secure thedamper element 431 to the inner end 478 of the blade 458. By way ofnon-limiting example, the aperture 441 is illustrated as a bracket pass455 and a flange pass 451. The flange pass 451 passes through theradially extending flange 435 and can have a flange pass diameter 453taken at the largest radial dimension of the flange pass 451. Thebracket pass 455 passes through the bracket 433 of the damper element431 and has a bracket pass diameter 457 taken at the radial largestdimension of the bracket pass 455. The flange pass 451, the bracket pass455, or the aperture 441 can be oversized compared to a fastenerdiameter 459 taken at the largest radial dimension of the flange pass451. Oversized can be, for example, more than 2% larger than thefastener diameter 459. Optionally, the fastener 439 can pass through aguide 461 that can extend into the bracket 433 or the radially extendingflange 435. A securing element 463 can be used to further adjust theposition of the fastener 439 within the flange pass 451, bracket pass455, or guide 461.

The honeycomb wear pad 447 can mount to the radially extending flange435 via the ring 437 of the damper element 431. The honeycomb wear pad447 an be secured to the ring 437 using any known fastening, molding, oradhering technique.

It should be understood that any combination of the geometry related tothe orientation of aspects disclosure herein is contemplated. Thevarying aspects of the disclosure discussed herein are for illustrativepurposes and not meant to be limiting.

The damper element 431 dampens the relative movement of the blades 458whose inner ends 478 are connected or secured by the ring 437. Therelative movement can include, but is not limited to relative radialmovement, relative tangential movement, or relative axial movement. Thedamper element 431 can also be used to direct, prevent, or controlairflow, for example, between the blades 458. It is contemplated thatthe damping element 431 or the ring 437 can dissipate kinetic energyfrom the inner ends 478 of the blades 458.

While cooling as discussed herein is optimal for a counter rotatingturbine, it can also be implemented in other types of turbine engines,such as, but not limited to, turbine engines with fan and boostersections, turbojets, or turbo engines.

Benefits associated with aspects of the disclosure herein includereduction of leakage of airflow between adjacent airfoils. That is, theorientation and application of the set of interlocking seals describedand illustrated herein control the flow of cooling fluid and help withwindage reduction in, for example, the LP turbine. The relativetemperature in the annular cavity with respect to the rotor is alsoreduced.

Another benefit of one or more portions of the damping element is thedissipation of at least a portion of the kinetic energy of the airfoils.The damping element can also serve as an interlock feature to secure theinner ends of the airfoils. Further, the damping element can limit atleast the relative axial movement between adjacent airfoils.

This written description uses examples to describe aspects of thedisclosure described herein, including the best mode, and also to enableany person skilled in the art to practice aspects of the disclosure,including making and using any devices or systems and performing anyincorporated methods. The patentable scope of aspects of the disclosureis defined by the claims, and may include other examples that occur tothose skilled in the art. Such other examples are intended to be withinthe scope of the claims if they have structural elements that do notdiffer from the literal language of the claims, or if they includeequivalent structural elements with insubstantial differences from theliteral languages of the claims.

Further aspects of the invention are provided by the subject matter ofthe following clauses:

1. A turbine engine comprising an inner rotor/stator having alongitudinal axis, an outer rotor circumscribing at least a portion ofthe inner rotor/stator and rotating about the longitudinal axis, andhaving at least one component comprising a plurality ofcircumferentially arranged and radially extending component segments,each component segment having first and second ends, and a damperelement securing the first and second to each other.

2. The turbine engine of any preceding clause wherein the damper elementcomprises a first channel on the first circumferential end of theconfronting pair, and a second channel on the second circumferential endof the confronting pair, with the first channel aligned with andconfronting the second channel to define a confronting channel pair, anda seal residing in both the first and second channels.

3. The turbine engine of any preceding clause wherein the confrontingchannel pair extend in a radial direction.

4. The turbine engine of any preceding clause wherein the length of theseal is less than the length of the confronting channel pair.

5. The turbine engine of any preceding clause wherein the seal has atleast one of a cross or rectangular cross section.

6. The turbine engine of any preceding clause wherein the componentsegments include passage segments extending between and opening onto thefirst and second circumferential ends at first and second openings todefine a confronting open pair of the first and second openings.

7. The turbine engine of any preceding clause wherein the passagesegments collectively form a circumferential passage.

8. The turbine engine of any preceding clause wherein the damper elementcomprises a tube extending through the confronting open pair of thefirst and second openings.

9. The turbine engine of any preceding clause wherein the tube extendsonly partially into passage segments of the pair of confronting ends.

10. The turbine engine of any preceding clause wherein the tubecomprises a spacer located between the confronting pairs of first andsecond circumferential ends.

11. The turbine engine of any preceding clause wherein the spacercircumscribes the tube.

12. The turbine engine of any preceding clause wherein the tube has across-sectional profile smaller than the passage segments.

13. The turbine engine of any preceding clause wherein the damperelement comprises a bracket coupling the inner ends of circumferentiallyadjacent inner ends.

14. The turbine engine of any preceding clause further comprising anaperture on at least one of the bracket and the inner ends, a fastenerextending through the aperture, with the aperture being oversizedrelative to the fastener.

15. The turbine engine of any preceding clause wherein the fastener hasa fastener cross-sectional shape, the aperture has an aperturecross-sectional shape, which is different than the fastenercross-sectional shape.

16. The turbine engine of any preceding clause wherein the fastenercross-sectional shape is circular and the aperture cross-sectional shapeis ovate.

17. The turbine engine of any preceding clause wherein the bracketcomprises a ring.

18. The turbine engine of any preceding clause wherein the inner endsdefine an inner band, with a radially extending flange and the ringmounts to the radially extending flange.

19. The turbine engine of any preceding clause further comprising ahoneycomb wear pad mounted to the radially extending flange.

20. The turbine engine of any preceding clause wherein the componentcomprises at least one of a shroud and airfoil.

What is claimed is:
 1. A turbine engine comprising: an innerrotor/stator having a longitudinal axis; an outer rotor circumscribingat least a portion of the inner rotor/stator and rotating about thelongitudinal axis, and having at least one component comprising aplurality of circumferentially arranged and radially extending componentsegments, each component segment having first and second ends; and adamper element securing the first and second ends to each other.
 2. Theturbine engine of claim 1 wherein the damper element comprises a firstchannel on the first circumferential end of the confronting pair, and asecond channel on the second circumferential end of the confrontingpair, with the first channel aligned with and confronting the secondchannel to define a confronting channel pair, and a seal residing inboth the first and second channels.
 3. The turbine engine of claim 2wherein the confronting channel pair extend in a radial direction. 4.The turbine engine of claim 3 wherein the length of the seal is lessthan the length of the confronting channel pair.
 5. The turbine engineof claim 4 wherein the seal has at least one of a cross or rectangularcross section.
 6. The turbine engine of claim 1 wherein the componentsegments include passage segments extending between and opening onto thefirst and second circumferential ends at first and second openings todefine a confronting open pair of the first and second openings.
 7. Theturbine engine of claim 6 wherein the passage segments collectively forma circumferential passage.
 8. The turbine engine of claim 6 wherein thedamper element comprises a tube extending through the confronting openpair of the first and second openings.
 9. The turbine engine of claim 8wherein the tube extends only partially into passage segments of thepair of confronting ends.
 10. The turbine engine of claim 8 wherein thetube comprises a spacer located between the confronting pairs of firstand second circumferential ends.
 11. The turbine engine of claim 10wherein the spacer circumscribes the tube.
 12. The turbine engine ofclaim 8 wherein the tube has a cross-sectional profile smaller than thepassage segments.
 13. The turbine engine of claim 1 wherein the damperelement comprises a bracket coupling the inner ends of circumferentiallyadjacent inner ends.
 14. The turbine engine of claim 13 furthercomprising an aperture on at least one of the bracket and the innerends, a fastener extending through the aperture, with the aperture beingoversized relative to the fastener.
 15. The turbine engine of claim 14wherein the fastener has a fastener cross-sectional shape, the aperturehas an aperture cross-sectional shape, which is different than thefastener cross-sectional shape.
 16. The turbine engine of claim 15wherein the fastener cross-sectional shape is circular and the aperturecross-sectional shape is ovate.
 17. The turbine engine of claim 13wherein the bracket comprises a ring.
 18. The turbine engine of claim 17wherein the inner ends define an inner band, with a radially extendingflange and the ring mounts to the radially extending flange.
 19. Theturbine engine of claim 18 further comprising a honeycomb wear padmounted to the radially extending flange.
 20. The turbine engine ofclaim 1 wherein the component comprises at least one of a shroud andairfoil.